CN107656253A - Electromagnetism vortex Synthetic Aperture Radar Echo emulation mode and device - Google Patents
Electromagnetism vortex Synthetic Aperture Radar Echo emulation mode and device Download PDFInfo
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- CN107656253A CN107656253A CN201710743228.3A CN201710743228A CN107656253A CN 107656253 A CN107656253 A CN 107656253A CN 201710743228 A CN201710743228 A CN 201710743228A CN 107656253 A CN107656253 A CN 107656253A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
- G01S13/88—Radar or analogous systems specially adapted for specific applications
- G01S13/89—Radar or analogous systems specially adapted for specific applications for mapping or imaging
- G01S13/90—Radar or analogous systems specially adapted for specific applications for mapping or imaging using synthetic aperture techniques, e.g. synthetic aperture radar [SAR] techniques
- G01S13/904—SAR modes
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S7/00—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00
- G01S7/02—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00 of systems according to group G01S13/00
- G01S7/40—Means for monitoring or calibrating
- G01S7/4052—Means for monitoring or calibrating by simulation of echoes
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
- G01S13/88—Radar or analogous systems specially adapted for specific applications
- G01S13/89—Radar or analogous systems specially adapted for specific applications for mapping or imaging
- G01S13/90—Radar or analogous systems specially adapted for specific applications for mapping or imaging using synthetic aperture techniques, e.g. synthetic aperture radar [SAR] techniques
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- Radar, Positioning & Navigation (AREA)
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- Electromagnetism (AREA)
- Radar Systems Or Details Thereof (AREA)
Abstract
This disclosure relates to a kind of electromagnetism vortex Synthetic Aperture Radar Echo emulation mode and device, methods described include：Obtain the simulation parameter of radar system；According to the simulation parameter of acquisition, the scenario parameters in target scene region are determined；According to the simulation parameter and the scenario parameters, electromagnetism vortex spaceborne SAR simulation echo-signal is obtained.The present disclosure proposes a kind of echo simulation method of electromagnetism vortex ripple for being applied to carry orbital angular momentum as radar emission signal, electromagnetism vortex polarization sensitive synthetic aperture radar system echo-signal can be depicted exactly using disclosed method, to realize that model basis is established in the processing of electromagnetism vortex synthetic aperture radar image-forming.
Description
Technical field
This disclosure relates to Radar Technology field, in particular it relates to which a kind of electromagnetism vortex Synthetic Aperture Radar Echo is imitated
True method.
Background technology
Synthetic aperture radar (Synthetic Aperture Radar, SAR) satellite was quickly grown in the last few years, due to
SAR satellites are not limited by factors such as weather, geography, times, can carry out round-the-clock, round-the-clock observation over the ground, and have
Certain penetration power, thus be widely used in military surveillance, mapping, resource detection, oceanographic observation, ecological monitoring,
Natural calamity monitoring, Quick rescue etc..
Spaceborne SAR simulation technology is that a kind of method with emulation studies the technology of SAR system, and it grinds SAR's
In work processed, have a very important role.The fidelity and simulation calculating efficiency of simulation result are to restrict SAR emulation technologies reality
Two central factors of border application, and this two big key element with the close phase of committed step in SAR echo simulations this SAR emulation
Close.
In correlation technique, SAR echo simulations are to be emulated common radar electromagnetic signal as radar emission signal,
It is only capable of obtaining the echo-signal of common radar electromagnetic signal.
The content of the invention
The purpose of the disclosure is to provide a kind of electromagnetism vortex Synthetic Aperture Radar Echo emulation mode, to solve correlation
The problem of in technology.
To achieve these goals, in a first aspect, the disclosure provides a kind of electromagnetism vortex Synthetic Aperture Radar Echo
Emulation mode, methods described include：
The simulation parameter of radar system is obtained, the simulation parameter information comprises at least：The running parameter and load of radar
The operational factor of machine equipment, wherein, one or more of following parameter of running parameter of the radar：Operating frequency of antenna,
Center of antenna visual angle, the signal bandwidth of transmission signal, the signal sampling rate of transmission signal, the pulse recurrence frequency of transmission signal,
The pulse width of transmission signal, transmission signal wavelength, radar start working time, orbital angular momentum pattern count and circular loop antenna
Radius, the orbital angular momentum are more than 0；The operational factor of the carrier aircraft equipment comprises at least：The flight speed of the carrier aircraft equipment
Degree, flying height；
According to the simulation parameter of acquisition, the scenario parameters in target scene region are determined, are joined below the scenario parameters
One or more of number：Distance is to point target number, orientation point target number, and distance is to point target interval and orientation point
Target interval, each target scattering coefficient；
According to the simulation parameter and the scenario parameters, electromagnetism vortex spaceborne SAR simulation echo-signal is obtained.
Alternatively, it is described according to the simulation parameter and the scenario parameters, obtain the echo containing electromagnetism vortex phase
The step of signal, includes：
According to the simulation parameter and the scenario parameters, echo-signal width of the point target k in each sampling instant is obtained
Angle value and phase value；
According to point target k in the echo signal amplitude value and phase value of each sampling instant, obtain the point target k and return
Electromagnetism vortex spaceborne SAR simulation echo-signal.
Alternatively, the point target k includes in the echo signal amplitude value of each sampling instant：Each orientation moment t(i)
Echo signal amplitude value Ak (i)；
The echo-signal phase value of each sampling instant includes：Each orientation moment t(i)With apart from time instant τ(j)Return
Ripple signal phase value φk (i,j)；
The echo-signal containing electromagnetism vortex phase that the point target k is returned is：
SEcho (i,j) k=Ak (i)×exp{φk (i,j)}
Wherein, i ∈ [1, Nver], j ∈ [Nmin,Nmax], NverFor orientation sampling number, [Nmin,Nmax] for point target k's
Distance is to echo samples range of signal.
Alternatively, each orientation moment t(i)Echo signal amplitude value Ak (i)For：
Wherein, Jα() represents Bessel function of the first kind, order α；K is wave number,fcFor antenna work
Working frequency；C is that light velocity a is circular antenna radius；For t(i)Moment carrier aircraft equipment and point target k elevation angle；σkIt is default
Target scattering coefficient；For antenna radiation pattern weights.
Alternatively, it is describedFor：
H=R0·cosθL
R0=Rref·sinθsquint
Wherein, RrefFor scene center oblique distance；A is circular loop antenna radius；xpFor according to antenna radiation pattern Bessel function
Signal formThe main lobe peak value position of determination；K is wave number；Rk (i)For t(i)Moment carrier aircraft equipment is with point target k's
Oblique distance；θLFor center of antenna visual angle.
Alternatively, the Rk (i)For：
Wherein,For orientation moment t(i), apart from time instant τ(j), the three-dimensional coordinates of point target k in space；
Wherein,For point target k and scene center, distance to relative position；For in point target k and scene
The heart, in the relative position of orientation；R0For carrier aircraft equipment and the nearest oblique distance of scene center；θLFor center of antenna visual angle；
Wherein, akIt is point target k in the sequence number of orientation, rkFor point target k distance to sequence number；
Wherein, V is the flying speed of carrier aircraft equipment；t(i)For the sampling instant corresponding to orientation sampled point i, i=
1,...,Nver；
Alternatively, methods described also includes：
By t(i)The Relative position vector R of moment aircraft and target point(i)(xsp,ysp,zsp) be converted under antenna coordinate system
Relative position vector
Obtain orientation off-axis angle θdev_a：
Wherein, arctan () represents arc tangent trigonometric function.
According to orientation off-axis angle θdev_a, obtain antenna radiation pattern weights；
Wherein, orientation off-axis angle θdev_aFor：θbeamFor beam main lobe width；.
Alternatively, the phase value φk (i,j)For：
Wherein, Rk (i)For t(i)Moment carrier aircraft equipment and point target k oblique distance；λ is the wavelength of circular antenna；BwFor signal band
It is wide；TrFor pulse width；C is the light velocity；α is orbital angular momentum pattern count；For t(i)Moment carrier aircraft equipment is with point target k's
Azimuth；It is describedFor：
Alternatively,
Wherein, RrefFor scene center oblique distance；fsFor signal sampling rate；NhorIt is distance to sampling number；TrIt is wide for pulse
Degree；Rk (i)For t(i)Moment carrier aircraft equipment and point target k oblique distance.
Second aspect, there is provided a kind of radar echo signal simulator, including：
Acquisition module, is configured as obtaining the simulation parameter of radar system, and the simulation parameter information comprises at least：Radar
Running parameter and carrier aircraft equipment operational factor, wherein, the running parameter of the radar includes：Operating frequency of antenna, day
Line centre visual angle, the signal bandwidth of transmission signal, the signal sampling rate of transmission signal, the pulse recurrence frequency of transmission signal, hair
Penetrate the pulse width of signal, transmission signal wavelength, radar start working time, orbital angular momentum pattern count and circular loop antenna half
Footpath, the orbital angular momentum are more than 0；The operational factor of the carrier aircraft equipment comprises at least：The flying speed of the carrier aircraft equipment,
Flying height；
Scenario parameters determining module, the simulation parameter according to acquisition is configured as, determines the field in target scene region
Scape parameter, the scenario parameters include：Distance is to point target number, orientation point target number, distance to point target interval and
Orientation point target interval, each target scattering coefficient；
Echo-signal acquisition module, it is configured as according to the simulation parameter and the scenario parameters, obtains electromagnetism and be vortexed
Spaceborne SAR simulation echo-signal.
The third aspect, there is provided a kind of computer-readable recording medium, be stored thereon with computer program, the program is processed
The step of device realizes method described above when performing.
Pass through above-mentioned technical proposal, it is proposed that a kind of electromagnetism vortex ripple for being applied to carry orbital angular momentum is as radar
The echo simulation method of transmission signal, electromagnetism vortex synthetic aperture radar system can be depicted exactly using disclosed method
System echo-signal, to realize that model basis is established in the processing of electromagnetism vortex synthetic aperture radar image-forming.
Other feature and advantage of the disclosure will be described in detail in subsequent specific embodiment part.
Brief description of the drawings
Accompanying drawing is for providing further understanding of the disclosure, and a part for constitution instruction, with following tool
Body embodiment is used to explain the disclosure together, but does not form the limitation to the disclosure.In the accompanying drawings：
Fig. 1 is the schematic diagram of the radar system of the embodiment of the disclosure one；
Fig. 2 is the schematic flow sheet of the radar echo signal emulation mode of the embodiment of the disclosure one；
Fig. 3 is the carrier aircraft equipment and ground space geometrical relationship figure of the embodiment of the disclosure one；
Fig. 4 is the Bessel function of the embodiment of the disclosure one with the different distribution character figure of pattern count；
Fig. 5 is the point target distribution schematic diagram in the target scene region of the embodiment of the disclosure one；
Fig. 6 is the schematic flow sheet that the radar echo signal of the embodiment of the disclosure one emulates point by point；
Fig. 7 is the electromagnetism vortex synthetic aperture radar echo amplitude figure of the embodiment of the disclosure one；
Fig. 8 is the electromagnetism vortex synthetic aperture radar echo real part figure of the embodiment of the disclosure one；
Fig. 9 is the block diagram of the radar echo signal simulator of the embodiment of the disclosure one；
Figure 10 is the block diagram of the device for being used for radar echo signal emulation of the embodiment of the disclosure one.
Embodiment
The embodiment of the disclosure is described in detail below in conjunction with accompanying drawing.It should be appreciated that this place is retouched
The embodiment stated is merely to illustrate and explained the disclosure, is not limited to the disclosure.
Referring to Fig. 1, for the schematic diagram of the radar system of the embodiment of the disclosure one.The radar system 100 includes：Radar 101,
Carrier aircraft equipment 102 and one or more point targets 103.
Radar 101 can be mounted in carrier aircraft equipment 102, follow carrier aircraft equipment 102 to be run with certain speed.Radar 101
Ranging or two-dimensional imaging etc. can be carried out to the point target 103 in beam area.Point target 103 can be arbitrary objects.
Radar 101 includes antenna 201, emitter 202, receiver 203, signal processing module 204 and transmitting-receiving conversion and opened
Close 205 etc..
Emitter 202 is used to produce electromagnetic energy.Electromagnetic energy sends antenna 201 to by transmit-receive switch 205.My god
Line 201 is used to electromagnetic energy being radiated in air, concentrates on a very narrow side and is upwardly formed beam propagation.Electromagnetic wave runs into ripple
After point target in beam, reflection will be produced along all directions, wherein, a part of electromagnetic energy is reflected back the direction of radar, quilt
Antenna 201 obtains.The electromagnetic energy that antenna 201 obtains sends receiver 203 to by transmit-receive switch 205, forms radar
Echo-signal.Receiver 203 sends signal processing module 204 to after the processing such as being filtered, amplifying to radar echo signal.
Signal processing module 204 obtains the information being included in echo.
In an embodiment of the disclosure, radar 101 can be synthetic aperture radar.Antenna 201 can be circular loop antenna 201,
It includes multiple bays circumferentially arranged, and the radius of circumference array is a, i.e., the radius of antenna 201 is a.Pass through circle
Loop antenna can produce electromagnetism vortex ripple, as a result, radar 101 can not only be in time domain, frequency domain and polarizing field internal modulation point mesh
Target information, and its specific orbital angular momentum (OAM) mode provides the new dimension of modulates information, obtains more points
The information of target.On the other hand, mode multiplexing potential greatly improves the spectrum utilization of system possessed by electromagnetism is vortexed
Rate, the inherent constraint present in conventional radar systems can not only be alleviated by the combination application of multi-mode, additionally it is possible to which realization is permitted
More new application model, it is obviously improved the detection efficiency over the ground of radar system.Electromagnetism vortex radar system possessed OAM is adjusted
Characteristic processed causes system to have robustness, the interference of traditional pressing type and forwarding for the broadband interference and ground return of same frequency range
Cheating interference is all difficult to influence electromagnetism vortex SAR system.Compared with conventional radar systems, electromagnetism vortex radar system has higher
Antijamming capability and counter-investigation ability.
It should be understood that the structure of the radar 101 of above-described embodiment is only schematical, on the basis of above-mentioned module, may be used also
Some modules progress function is integrated, or reduces certain module etc., the disclosure is not restricted to this.
In the embodiment of the present disclosure, scene areas, point target quantity and position are being determined, the running parameter of radar, and
During the operational factor of carrier aircraft equipment, the echo-signal containing electromagnetism vortex phase is obtained.
Referring to Fig. 2, in an embodiment of the disclosure, radar echo signal emulation mode comprises the following steps：
In the step s 21, simulation parameter is obtained.Simulation parameter comprises at least：The running parameter of radar and carrier aircraft equipment
Operational factor.
In one embodiment, work of the parameter of actual radar as the radar needed for emulation can be obtained from Relational database
Make parameter.For example, the Relational database can store actual radar system (for example, radar system shown in above-mentioned Fig. 1) work fortune
Parameter during row, these parameters may include：Operating frequency of antenna fc, center of antenna view angle thetaL, the signal bandwidth B of transmission signalw,
The signal sampling rate f of transmission signals, the pulse recurrence frequency PRF of transmission signal, the pulse width T of transmission signalr, transmission signal
Wavelength X, radar start working time Tall, orbital angular momentum pattern count α and circular loop antenna radius a etc..For carrier aircraft equipment
Operational factor, the parameter of carrier aircraft equipment actual motion can be obtained, made for example, receiving the actual operation parameters that carrier aircraft equipment returns
To emulate the operational factor of described carrier aircraft equipment, these parameters can include：The flying speed V of carrier aircraft equipment, flying height
H。
It should be understood that in certain embodiments, can also the parameter of actual radar and the operational factor of actual carrier aircraft equipment be
Foundation, simulation parameter is pre-set.
In step S22, according to the simulation parameter of acquisition, the scenario parameters in target scene region are determined.
After being determined due to simulation parameter, the scope that the transmission signal of radar can be irradiated to determines, therefore, the disclosure is implemented
In example, according to simulation parameter, the scenario parameters of emulation are further determined that.Scenario parameters comprise at least：Distance is to point target number
Nr, orientation point target number Na, distance is to point target interval drWith orientation point target interval da, each target scattering coefficient σk。
In one embodiment, referring to Fig. 3, the radar being mounted in carrier aircraft equipment, with the flight of carrier aircraft equipment, radar
The range of exposures of transmission signal is target scene region.The size in the target scene region is by scene orientation length and scene
Distance determines to width.Wherein, scene orientation length is relevant with the radar start working time of carrier aircraft equipment and flying speed,
And scene distance is related to the radiation scope of the circular antenna of radar to width.Referring to formula (1) to formula (4)：
Wa=V × Tall (1)
Wr=θbeam×Rref (2)
Wherein, TallStarted shooting the working time for radar；fcFor operating frequency of antenna；C is the light velocity, and its value is 3 × 108(m/s)；
K is wave number；A is circular loop antenna radius；xz1For the signal form according to antenna radiation pattern Bessel functionThe side of acquisition
To the 1st zero point of figure；xz2For the signal form according to antenna radiation pattern Bessel functionThe directional diagram of acquisition the 2nd
Zero point；RrefFor the scene center oblique distance in target scene region, i.e., according to the center of the scene areas of the determination in target scene region
Apart from the oblique distance of carrier aircraft equipment 102.
In target scene regional extent, N is setr×NaIndividual point target, wherein, NrIt is distance to point target number, NaFor
Orientation point target number, distance is to point target at intervals of dr, orientation point target is at intervals of da.Distance is to point target interval dr
With distance to point target number NrProduct be less than or equal to scene distance to width Wr。
In one embodiment, fc=9.6GHz, θL=35 °, V=250m/s, Rref=30000m, fs=140MHz, Bw
=100MHz, PRF=2000Hz, Tr=10 μ s, Nr=3, Na=3, dr=200m, da=1500m, α=7, a=30 λ.
In step S23, according to simulation parameter and scenario parameters, the echo-signal containing electromagnetism vortex phase is obtained.
Thus, by the emulation mode of the embodiment of the present disclosure, the echo-signal containing electromagnetism vortex phase can be got.Base
In the echo-signal containing electromagnetism vortex phase, the imaging of point target can be further carried out, obtains the position letter of point target
Breath etc..By the embodiment of the present disclosure, in the case where not needing radar emission to receive hardware, according to the information in simulating scenes region
With radar simulation parameter information, the echo-signal containing electromagnetism vortex phase, escapable cost are obtained；And the embodiment of the present disclosure obtains
What is got is the echo-signal containing electromagnetism vortex phase, can obtain the information of more point targets accordingly, be further
Point target is imaged and analysis provides support.
In one embodiment, it is also necessary to sampling number is determined, to determine that the signal of echo-signal is counted.Sampling number bag
Include：Distance is to sampling number NhorAnd orientation sampling number Nver.Sampling number can be according to signal sampling rate fsWith synthesis hole
The footpath time determines.
Hereinafter, (exemplified by point target k) echo-signal, illustrate to obtain containing electricity in above-mentioned steps S23 by a point target
The echo-signal of vortex phase.Referring to formula (1), in an embodiment of the disclosure, it can obtain according to formula (5) and contain electromagnetism
The echo-signal of the point target k reflections of vortex phase.
SEcho (i,j) k=Ak (i)×exp{φk (i,j)} (5)
Wherein, i ∈ [1, Nver], j ∈ [Nmin,Nmax], NverFor orientation sampling number, [Nmin,Nmax] for distance to return
Ripple sampled signal scope, thus, SEchoFor the echo-signal space matrix of i rows j row, i.e. each matrix element is used for depositing one
The complex data of individual sampled point；Ak (i)For orientation t(i)The range value of the point target k at moment echo-signal；φk (i,j)For orientation t(i)Moment, distance τ(j)The phase value of the point target k at moment echo-signal, k=1 ..., Na·Nr。
The acquisition of the range value of echo-signal
In one embodiment, according to Bessel function of the first kind, operating frequency of antenna is orbital angular momentum pattern count, pre-
If target scattering coefficient, antenna radiation pattern weights and the elevation angle of carrier aircraft equipment and point target, orientation t is obtained(i)The point at moment
The range value of target k echo-signalAk (i) 。
Referring to formula (6), in one embodiment, orientation t(i)The range value of the point target k at moment echo-signal is：
Wherein, Jα() represents Bessel function of the first kind, and order is α (orbital angular momentum pattern count)；K is wave number；A is
Circular antenna radius；For t(i)Moment carrier aircraft equipment and point target k elevation angle；σkFor goal-selling scattering coefficient；For
Antenna radiation pattern weights.
Referring to formula (7) to (10)：
H=R0·cosθL (8)
R0=Rref·sinθsquint (9)
Wherein, RrefFor scene center oblique distance；A is circular loop antenna radius；xpFor according to antenna radiation pattern Bessel function
Signal formThe main lobe peak value position of determination, referring to Fig. 4, α is different, according to antenna radiation pattern Bessel function
The main lobe peak value position that signal form determines just differs；K is wave number；Rk (i)For t(i)Moment carrier aircraft equipment and point target k
Oblique distance, referring to formula (11)：
Wherein,For orientation t(i)Moment, distance τ(j)Moment, the three-dimensional coordinates of point target k in space.
Referring to formula (12)：
Wherein,For point target k and scene center, distance to relative position；For in point target k and scene
The heart, in the relative position of orientation；R0For carrier aircraft equipment and the nearest oblique distance of scene center；θLFor center of antenna visual angle.Referring to formula
(13)：
Wherein, akIt is point target k in the sequence number of orientation, rkFor point target k distance to sequence number.Referring to Fig. 5, at this
In disclosed embodiment, by each point target according to orientation and distance to being numbered.It is using the quantity of point target as 9
Example, in Fig. 3 the orientation sequence number of first point target in the upper left corner and distance to sequence number be 1, the side of the point target in the lower right corner
To position sequence number and distance to sequence number be respectively Na (being 9) and Nr (as 9).Thus, according to formula (10), can respectively obtain a little
Target k and scene center, distance to relative position, and point target k and scene center, in the relative position of orientation.
In one embodiment, referring to formula (14), above-mentioned formula (8) and above-mentioned formula (9), the x in above-mentioned formula (11)s, ys,
zsFor：
Wherein, V is the flying speed of carrier aircraft equipment；t(i)For the sampling instant corresponding to orientation sampled point i, i=
1,...,Nver.Referring to formula (15) and (16)：
Wherein, NverFor orientation sampling number；PRF is pulse recurrence frequency；RrefFor scene center oblique distance；V is carrier aircraft
The flying speed of equipment；θsquintReferring to formula (10) Suo Shi.
The acquisition of the phase value of echo-signal
In one embodiment, orientation t is obtained according to formula (17)(i)Moment, distance τ(j)The phase of the echo-signal at moment
Value φk (i,j)：
Wherein, Rk (i)For t(i)Moment carrier aircraft equipment and point target k oblique distance, R can be obtained referring to formula (11)-(14)k (i)；λ
For the wavelength of circular antenna；BwFor signal bandwidth；TrFor pulse width；C is the light velocity；α is orbital angular momentum pattern count；For t(i)Moment carrier aircraft equipment and point target k azimuth.
Referring to formula (18), and above-mentioned formula (8) is to formula (10), and formula (15)：
Wherein, V is the flying speed of carrier aircraft equipment.
Obtain antenna radiation pattern weights
First, by t(i)Moment carrier aircraft equipment and point target k Relative position vector R(i)(xsp,ysp,zsp) be converted to antenna
Relative position vector under coordinate systemReferring to formula (19)：
Wherein, x can be obtained according to formula (12) to (14)sp, yspAnd zsp；θLFor center of antenna visual angle.
Then, orientation off-axis angle θ is obtaineddev_a, referring to formula (20)：
Wherein, arctan () represents arc tangent trigonometric function.
3rd, according to orientation off-axis angle θdev_a, obtain antenna radiation pattern weights.
In an embodiment of the disclosure, if θdev_aLess than beam main lobe width θbeam, then in range of exposures, according to pre-
The direction graph type first defined determinesIf directional diagram is actual measurement directional diagram, even θdev_aMore than or equal to beam main lobe width
θbeam, then can be obtained according to the direction map file of reading.In one embodiment, if using theory orientation figure,Can be with
It is expressed as：
Determine that distance uses range of signal [N to echomin,Nmax], referring to formula (22)：
Wherein, RrefFor scene center oblique distance；fsFor signal sampling rate；NhorIt is distance to sampling number；TrIt is wide for pulse
Degree；Rk (i)For t(i)Moment carrier aircraft equipment and point target k oblique distance, R can be obtained referring to formula (11)-(16)k (i)。
Referring to formula (23), the τ in formula (17)(j)For：
Referring to Fig. 6, for the schematic flow sheet of the point-by-point emulation of the radar echo signal of the embodiment of the disclosure one.In step
In S61, simulation parameter is obtained.In step S62, echo-signal space matrix is opened up.The size of echo-signal space matrix by
Distance determines to sampling number and orientation sampling number.In step S63, according to simulation parameter, scenario parameters are determined.In step
In rapid S64, according to sampled point, start to emulate point by point.In step S65, judge whether the size of direction position sampled point is less than side
To for sampling number, if being less than, direction position sampled point is added one, and in step S66, calculates current time, carrier aircraft equipment
Flight position；In step S67, point target emulates point by point；In step S68, judge whether point target k is less than distance to point
The product of target numbers and orientation point target number, it be not calculating current time relative position arrow in S69 if being less than
Amount, oblique distance, elevation angle and azimuth.In step S70, distance is to point-by-point emulation, in step S71, judge j whether be less than away from
Descriscent sampling number, if being less than, computer azimuth moment distance is to echo samples range of signal in step S72, in step S73
In, echo signal amplitude value and phase value are calculated, is imitated in step S74 according to echo signal amplitude value and phase value output echo
True result.
Referring to the range value figure that Fig. 7 is the radar echo signal being vortexed comprising electromagnetism that the embodiment of the disclosure one obtains.Ginseng
See the radar echo signal real part figure being vortexed comprising electromagnetism that Fig. 8 is the embodiment of the disclosure one.
The embodiment of the present disclosure proposes a kind of electromagnetism vortex ripple for being applied to carry orbital angular momentum as radar emission
Signal echo emulation mode, electromagnetism vortex SAR system echo-signal can be depicted exactly using disclosed method, in fact
Model basis is established in existing High Resolution SAR Imaging processing.
Referring to Fig. 9, for the block diagram of the radar echo signal simulator of the embodiment of the disclosure one, the device includes：
Acquisition module 901, is configured as obtaining the simulation parameter of radar system, and the simulation parameter information comprises at least：
The running parameter of radar and the operational factor of carrier aircraft equipment, wherein, the running parameter of the radar is included in following parameter
One or more：Operating frequency of antenna, center of antenna visual angle, the signal bandwidth of transmission signal, the pulse of transmission signal repeat frequency
Rate, the pulse width of transmission signal, orbital angular momentum pattern count and circular loop antenna radius, the orbital angular momentum are more than 0；Institute
The operational factor for stating carrier aircraft equipment comprises at least：The flying speed of the carrier aircraft equipment；
Scenario parameters determining module 902, the simulation parameter according to acquisition is configured as, determines target scene region
Scenario parameters, the scenario parameters include one or more of following parameter：Distance is to point target number, orientation point target
Number, distance is to point target interval and orientation point target interval, each target scattering coefficient；
Echo-signal acquisition module 903, it is configured as, according to the simulation parameter and the scenario parameters, obtaining containing electricity
The echo-signal of vortex phase.
On the device in above-described embodiment, wherein modules perform the concrete mode of operation in relevant this method
Embodiment in be described in detail, explanation will be not set forth in detail herein.
Figure 10 is a kind of for performing above-mentioned radar echo signal emulation mode according to an exemplary embodiment
The block diagram of device.As shown in Figure 10, the device 1000 can include：Processor 1022, its quantity can be one or more, with
And memory 1032, for storing the computer program that can be performed by processor 1022.The computer stored in memory 1032
Program can include it is one or more each correspond to the module of one group of instruction.In addition, processor 1022 can be by
It is configured to perform the computer program, to perform above-mentioned radar echo signal emulation mode.
In addition, device 1000 can also include power supply module 1026 and communication component 1050, the power supply module 1026 can be with
The power management of performs device 1000 is configured as, the communication component 1050 can be configured as realizing the logical of electronic equipment 1000
Letter, for example, wired or wireless communication.In addition, the device 1000 can also include input/output (I/O) interface 1058.At one
In embodiment, the information such as simulation parameter can be obtained by input/output (I/O) interface 1058.Device 1000 can operate base
In the operating system for being stored in memory 1032, such as Windows ServerTM, Mac OS XTM, UnixTM, LinuxTM etc.
Deng.
In a further exemplary embodiment, a kind of computer-readable recording medium including programmed instruction, example are additionally provided
Such as include the memory 1032 of programmed instruction, said procedure instruction can be performed above-mentioned to complete by the processor 1022 of device 1000
Radar echo signal emulation mode.
The preferred embodiment of the disclosure is described in detail above in association with accompanying drawing, still, the disclosure is not limited to above-mentioned reality
The detail in mode is applied, in the range of the technology design of the disclosure, a variety of letters can be carried out to the technical scheme of the disclosure
Monotropic type, these simple variants belong to the protection domain of the disclosure.
It is further to note that each particular technique feature described in above-mentioned embodiment, in not lance
In the case of shield, it can be combined by any suitable means.In order to avoid unnecessary repetition, the disclosure to it is various can
The combination of energy no longer separately illustrates.
In addition, it can also be combined between a variety of embodiments of the disclosure, as long as it is without prejudice to originally
Disclosed thought, it should equally be considered as disclosure disclosure of that.
Claims (10)
1. a kind of electromagnetism vortex Synthetic Aperture Radar Echo emulation mode, it is characterised in that methods described includes：
The simulation parameter of radar system is obtained, the simulation parameter information comprises at least：The running parameter and carrier aircraft of radar are set
Standby operational factor, wherein, the running parameter of the radar includes one or more of following parameter：Operating frequency of antenna,
Center of antenna visual angle, the signal bandwidth of transmission signal, the signal sampling rate of transmission signal, the pulse recurrence frequency of transmission signal,
The pulse width of transmission signal, radar start working time, orbital angular momentum pattern count and circular loop antenna radius, the track
Angular momentum is more than 0；The operational factor of the carrier aircraft equipment comprises at least：Flying speed, the flying height of the carrier aircraft equipment；
According to the simulation parameter of acquisition, the scenario parameters in target scene region are determined, the scenario parameters include following ginseng
One or more of number：Distance is to point target number, orientation point target number, and distance is to point target interval and orientation point
Target interval, each target scattering coefficient；
According to the simulation parameter and the scenario parameters, electromagnetism vortex spaceborne SAR simulation echo-signal is obtained.
2. according to the method for claim 1, it is characterised in that it is described according to the simulation parameter and the scenario parameters,
The step of obtaining power taking vortex spaceborne SAR simulation echo-signal includes：
According to the simulation parameter and the scenario parameters, echo signal amplitude values of the point target k in each sampling instant is obtained
And phase value；
According to point target k in the echo signal amplitude value and phase value of each sampling instant, the electricity that the point target k is returned is obtained
Vortex spaceborne SAR simulation echo-signal.
3. according to the method for claim 2, it is characterised in that echo-signals of the point target k in each sampling instant
Range value includes：Each orientation moment t(i)Echo signal amplitude value Ak (i)；
The echo-signal phase value of each sampling instant includes：Each orientation moment t(i)With apart from time instant τ(j)Echo letter
Number phase value φk (i,j)；
The echo-signal containing electromagnetism vortex phase that the point target k is returned is：
SEcho (i,j) k=Ak (i)×exp{φk (i,j)}
Wherein, i ∈ [1, Nver], j ∈ [Nmin,Nmax], NverFor orientation sampling number, [Nmin,Nmax] be point target k distance
To echo samples range of signal.
4. according to the method for claim 3, it is characterised in that point target k each orientation moment t(i)Echo-signal
Range value Ak (i)For：
<mrow>
<msup>
<msub>
<mi>A</mi>
<mi>k</mi>
</msub>
<mrow>
<mo>(</mo>
<mi>i</mi>
<mo>)</mo>
</mrow>
</msup>
<mo>=</mo>
<msub>
<mi>&sigma;</mi>
<mi>k</mi>
</msub>
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<mi>w</mi>
<mi>a</mi>
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<msubsup>
<mi>J</mi>
<mi>&alpha;</mi>
<mn>2</mn>
</msubsup>
<mrow>
<mo>(</mo>
<mi>K</mi>
<mo>&times;</mo>
<mi>a</mi>
<mo>&times;</mo>
<msubsup>
<mi>sin&theta;</mi>
<mrow>
<mi>O</mi>
<mi>A</mi>
<mi>M</mi>
</mrow>
<mrow>
<mo>(</mo>
<mi>i</mi>
<mo>)</mo>
</mrow>
</msubsup>
<mo>)</mo>
</mrow>
</mrow>
Wherein, Jα() represents Bessel function of the first kind, order α；K is wave number,fcFor Antenna Operation frequency
Rate；C is the light velocity；A is circular antenna radius；For t(i)Moment carrier aircraft equipment and point target k elevation angle；σkTo preset mesh
Mark scattering coefficient；For antenna radiation pattern weights.
5. according to the method for claim 4, it is characterised in that describedFor：
<mrow>
<msubsup>
<mi>&theta;</mi>
<mrow>
<mi>O</mi>
<mi>A</mi>
<mi>M</mi>
</mrow>
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<mo>)</mo>
</mrow>
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<mo>=</mo>
<mi>arccos</mi>
<mrow>
<mo>(</mo>
<mo>-</mo>
<mfrac>
<mi>H</mi>
<mrow>
<msup>
<msub>
<mi>R</mi>
<mi>k</mi>
</msub>
<mrow>
<mo>(</mo>
<mi>i</mi>
<mo>)</mo>
</mrow>
</msup>
</mrow>
</mfrac>
<mo>)</mo>
</mrow>
</mrow>
H=R0·cosθL
R0=Rref·sinθsquint
<mrow>
<msub>
<mi>&theta;</mi>
<mrow>
<mi>s</mi>
<mi>q</mi>
<mi>u</mi>
<mi>i</mi>
<mi>n</mi>
<mi>t</mi>
</mrow>
</msub>
<mo>=</mo>
<mi>arcsin</mi>
<mrow>
<mo>(</mo>
<mfrac>
<msub>
<mi>x</mi>
<mi>p</mi>
</msub>
<mrow>
<mi>K</mi>
<mo>&times;</mo>
<mi>a</mi>
</mrow>
</mfrac>
<mo>)</mo>
</mrow>
</mrow>
Wherein, RrefFor scene center oblique distance；A is circular loop antenna radius；xpFor the signal according to antenna radiation pattern Bessel function
FormThe main lobe peak value position of determination；K is wave number；Rk (i)For t(i)Moment carrier aircraft equipment is oblique with point target k's
Away from；θLFor center of antenna visual angle.
6. according to the method for claim 5, it is characterised in that the Rk (i)For：
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<msub>
<mi>R</mi>
<mi>k</mi>
</msub>
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<mo>=</mo>
<msqrt>
<mrow>
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<mi>x</mi>
<mrow>
<mi>s</mi>
<mi>p</mi>
</mrow>
<mn>2</mn>
</msubsup>
<mo>+</mo>
<msubsup>
<mi>y</mi>
<mrow>
<mi>s</mi>
<mi>p</mi>
</mrow>
<mn>2</mn>
</msubsup>
<mo>+</mo>
<msubsup>
<mi>z</mi>
<mrow>
<mi>s</mi>
<mi>p</mi>
</mrow>
<mn>2</mn>
</msubsup>
</mrow>
</msqrt>
<mo>=</mo>
<msqrt>
<mrow>
<msup>
<mrow>
<mo>(</mo>
<msubsup>
<mi>x</mi>
<mi>p</mi>
<mrow>
<mo>(</mo>
<mi>k</mi>
<mo>)</mo>
</mrow>
</msubsup>
<mo>-</mo>
<msubsup>
<mi>x</mi>
<mi>s</mi>
<mrow>
<mo>(</mo>
<mi>k</mi>
<mo>)</mo>
</mrow>
</msubsup>
<mo>)</mo>
</mrow>
<mn>2</mn>
</msup>
<mo>+</mo>
<msup>
<mrow>
<mo>(</mo>
<msubsup>
<mi>y</mi>
<mi>p</mi>
<mrow>
<mo>(</mo>
<mi>k</mi>
<mo>)</mo>
</mrow>
</msubsup>
<mo>-</mo>
<msubsup>
<mi>y</mi>
<mi>s</mi>
<mrow>
<mo>(</mo>
<mi>k</mi>
<mo>)</mo>
</mrow>
</msubsup>
<mo>)</mo>
</mrow>
<mn>2</mn>
</msup>
<mo>+</mo>
<msup>
<mrow>
<mo>(</mo>
<msubsup>
<mi>z</mi>
<mi>p</mi>
<mrow>
<mo>(</mo>
<mi>k</mi>
<mo>)</mo>
</mrow>
</msubsup>
<mo>-</mo>
<msubsup>
<mi>z</mi>
<mi>s</mi>
<mrow>
<mo>(</mo>
<mi>k</mi>
<mo>)</mo>
</mrow>
</msubsup>
<mo>)</mo>
</mrow>
<mn>2</mn>
</msup>
</mrow>
</msqrt>
</mrow>
Wherein,For orientation moment t(i), apart from time instant τ(j), the three-dimensional coordinates of point target k in space；
<mfenced open = "{" close = "">
<mtable>
<mtr>
<mtd>
<mrow>
<msubsup>
<mi>x</mi>
<mi>p</mi>
<mrow>
<mo>(</mo>
<mi>k</mi>
<mo>)</mo>
</mrow>
</msubsup>
<mo>=</mo>
<msub>
<mi>R</mi>
<mn>0</mn>
</msub>
<msub>
<mi>sin&theta;</mi>
<mi>L</mi>
</msub>
<mo>+</mo>
<msubsup>
<mi>P</mi>
<mi>r</mi>
<mrow>
<mo>(</mo>
<mi>k</mi>
<mo>)</mo>
</mrow>
</msubsup>
</mrow>
</mtd>
</mtr>
<mtr>
<mtd>
<mrow>
<msubsup>
<mi>y</mi>
<mi>p</mi>
<mrow>
<mo>(</mo>
<mi>k</mi>
<mo>)</mo>
</mrow>
</msubsup>
<mo>=</mo>
<msubsup>
<mi>P</mi>
<mi>a</mi>
<mrow>
<mo>(</mo>
<mi>k</mi>
<mo>)</mo>
</mrow>
</msubsup>
</mrow>
</mtd>
</mtr>
<mtr>
<mtd>
<mrow>
<msubsup>
<mi>z</mi>
<mi>p</mi>
<mrow>
<mo>(</mo>
<mi>k</mi>
<mo>)</mo>
</mrow>
</msubsup>
<mo>=</mo>
<mn>0</mn>
</mrow>
</mtd>
</mtr>
</mtable>
</mfenced>
Wherein,For point target k and scene center, distance to relative position；For point target k and scene center,
The relative position of orientation；R0For carrier aircraft equipment and the nearest oblique distance of scene center；θLFor center of antenna visual angle；
<mfenced open = "{" close = "">
<mtable>
<mtr>
<mtd>
<msubsup>
<mi>P</mi>
<mi>a</mi>
<mrow>
<mo>(</mo>
<mi>k</mi>
<mo>)</mo>
</mrow>
</msubsup>
<mo>=</mo>
<msub>
<mi>d</mi>
<mi>a</mi>
</msub>
<mo>&CenterDot;</mo>
<mo>(</mo>
<msub>
<mi>a</mi>
<mi>k</mi>
</msub>
<mo>-</mo>
<msub>
<mi>N</mi>
<mi>a</mi>
</msub>
<mo>/</mo>
<mn>2</mn>
<mo>)</mo>
</mtd>
</mtr>
<mtr>
<mtd>
<msubsup>
<mi>P</mi>
<mi>r</mi>
<mrow>
<mo>(</mo>
<mi>k</mi>
<mo>)</mo>
</mrow>
</msubsup>
<mo>=</mo>
<msub>
<mi>d</mi>
<mi>r</mi>
</msub>
<mo>&CenterDot;</mo>
<mo>(</mo>
<msub>
<mi>r</mi>
<mi>k</mi>
</msub>
<mo>-</mo>
<msub>
<mi>N</mi>
<mi>r</mi>
</msub>
<mo>/</mo>
<mn>2</mn>
<mo>)</mo>
</mtd>
</mtr>
</mtable>
</mfenced>
Wherein, akIt is point target k in the sequence number of orientation, rkFor point target k distance to sequence number；
<mfenced open = "{" close = "">
<mtable>
<mtr>
<mtd>
<msub>
<mi>x</mi>
<mi>s</mi>
</msub>
<mo>=</mo>
<mn>0</mn>
</mtd>
</mtr>
<mtr>
<mtd>
<msub>
<mi>y</mi>
<mi>s</mi>
</msub>
<mo>=</mo>
<mi>V</mi>
<mo>&CenterDot;</mo>
<msup>
<mi>t</mi>
<mrow>
<mo>(</mo>
<mi>i</mi>
<mo>)</mo>
</mrow>
</msup>
</mtd>
</mtr>
<mtr>
<mtd>
<mrow>
<msub>
<mi>z</mi>
<mi>s</mi>
</msub>
<mo>=</mo>
<mi>H</mi>
</mrow>
</mtd>
</mtr>
</mtable>
</mfenced>
Wherein, V is the flying speed of carrier aircraft equipment；t(i)For the sampling instant corresponding to orientation sampled point i, i=1 ...,
Nver；
<mrow>
<msup>
<mi>t</mi>
<mrow>
<mo>(</mo>
<mi>i</mi>
<mo>)</mo>
</mrow>
</msup>
<mo>=</mo>
<mfrac>
<mrow>
<mi>i</mi>
<mo>-</mo>
<msub>
<mi>N</mi>
<mrow>
<mi>v</mi>
<mi>e</mi>
<mi>r</mi>
</mrow>
</msub>
<mo>/</mo>
<mn>2</mn>
</mrow>
<mrow>
<mi>P</mi>
<mi>R</mi>
<mi>F</mi>
</mrow>
</mfrac>
<mo>+</mo>
<msub>
<mi>t</mi>
<mi>c</mi>
</msub>
</mrow>
<mrow>
<msub>
<mi>t</mi>
<mi>c</mi>
</msub>
<mo>=</mo>
<mfrac>
<mrow>
<msub>
<mi>R</mi>
<mrow>
<mi>r</mi>
<mi>e</mi>
<mi>f</mi>
</mrow>
</msub>
<mo>&times;</mo>
<msub>
<mi>sin&theta;</mi>
<mrow>
<mi>s</mi>
<mi>q</mi>
<mi>u</mi>
<mi>i</mi>
<mi>n</mi>
<mi>t</mi>
</mrow>
</msub>
</mrow>
<mi>V</mi>
</mfrac>
<mo>.</mo>
</mrow>
7. according to the method for claim 4, it is characterised in that methods described also includes：
By t(i)The Relative position vector R of moment aircraft and target point(i)(xsp,ysp,zsp) be converted to it is relative under antenna coordinate system
Position vector
Obtain orientation off-axis angle θdev_a：
<mrow>
<msub>
<mi>&theta;</mi>
<mrow>
<mi>d</mi>
<mi>e</mi>
<mi>v</mi>
<mo>_</mo>
<mi>a</mi>
</mrow>
</msub>
<mo>=</mo>
<mi>arctan</mi>
<mrow>
<mo>(</mo>
<mfrac>
<msubsup>
<mi>x</mi>
<mrow>
<mi>s</mi>
<mi>p</mi>
</mrow>
<mo>&prime;</mo>
</msubsup>
<msubsup>
<mi>y</mi>
<mrow>
<mi>s</mi>
<mi>p</mi>
</mrow>
<mo>&prime;</mo>
</msubsup>
</mfrac>
<mo>)</mo>
</mrow>
</mrow>
Wherein, arctan () represents arc tangent trigonometric function.
According to orientation off-axis angle θdev_a, obtain antenna radiation pattern weights；
Wherein, orientation off-axis angle θdev_aFor：θbeamFor beam main lobe width.
8. according to the method for claim 3, it is characterised in that the phase value φk (i,j)For：
Wherein, Rk (i)For t(i)Moment carrier aircraft equipment and point target k oblique distance；λ is the wavelength of circular antenna；BwFor signal bandwidth；
TrFor pulse width；C is the light velocity；α is orbital angular momentum pattern count；For t(i)Moment carrier aircraft equipment and point target k orientation
Angle；It is describedFor：
9. according to the method for claim 8, it is characterised in that
<mfenced open = "{" close = "">
<mtable>
<mtr>
<mtd>
<msub>
<mi>N</mi>
<mi>min</mi>
</msub>
<mo>=</mo>
<mfrac>
<mrow>
<msup>
<msub>
<mi>R</mi>
<mi>k</mi>
</msub>
<mrow>
<mo>(</mo>
<mi>i</mi>
<mo>)</mo>
</mrow>
</msup>
<mo>-</mo>
<msub>
<mi>R</mi>
<mrow>
<mi>r</mi>
<mi>e</mi>
<mi>f</mi>
</mrow>
</msub>
</mrow>
<mrow>
<mi>c</mi>
<mo>/</mo>
<mn>2</mn>
</mrow>
</mfrac>
<mo>&CenterDot;</mo>
<msub>
<mi>f</mi>
<mi>s</mi>
</msub>
<mo>+</mo>
<mfrac>
<msub>
<mi>N</mi>
<mrow>
<mi>h</mi>
<mi>o</mi>
<mi>r</mi>
</mrow>
</msub>
<mn>2</mn>
</mfrac>
<mo>-</mo>
<mfrac>
<mrow>
<msub>
<mi>T</mi>
<mi>r</mi>
</msub>
<mo>&CenterDot;</mo>
<msub>
<mi>f</mi>
<mi>s</mi>
</msub>
</mrow>
<mn>2</mn>
</mfrac>
</mtd>
</mtr>
<mtr>
<mtd>
<msub>
<mi>N</mi>
<mrow>
<mi>m</mi>
<mi>a</mi>
<mi>x</mi>
</mrow>
</msub>
<mo>=</mo>
<mfrac>
<mrow>
<msup>
<msub>
<mi>R</mi>
<mi>k</mi>
</msub>
<mrow>
<mo>(</mo>
<mi>i</mi>
<mo>)</mo>
</mrow>
</msup>
<mo>-</mo>
<msub>
<mi>R</mi>
<mrow>
<mi>r</mi>
<mi>e</mi>
<mi>f</mi>
</mrow>
</msub>
</mrow>
<mrow>
<mi>c</mi>
<mo>/</mo>
<mn>2</mn>
</mrow>
</mfrac>
<mo>&CenterDot;</mo>
<msub>
<mi>f</mi>
<mi>s</mi>
</msub>
<mo>+</mo>
<mfrac>
<msub>
<mi>N</mi>
<mrow>
<mi>h</mi>
<mi>o</mi>
<mi>r</mi>
</mrow>
</msub>
<mn>2</mn>
</mfrac>
<mo>+</mo>
<mfrac>
<mrow>
<msub>
<mi>T</mi>
<mi>r</mi>
</msub>
<mo>&CenterDot;</mo>
<msub>
<mi>f</mi>
<mi>s</mi>
</msub>
</mrow>
<mn>2</mn>
</mfrac>
</mtd>
</mtr>
</mtable>
</mfenced>
Wherein, RrefFor scene center oblique distance；fsFor signal sampling rate；NhorIt is distance to sampling number；TrFor pulse width；Rk (i)For t(i)Moment carrier aircraft equipment and point target k oblique distance.
A kind of 10. radar echo signal simulator, it is characterised in that including：
Acquisition module, is configured as obtaining the simulation parameter of radar system, and the simulation parameter information comprises at least：The work of radar
Make the operational factor of parameter and carrier aircraft equipment, wherein, the running parameter of the radar includes：Operating frequency of antenna, in antenna
Heart visual angle, the signal bandwidth of transmission signal, the signal sampling rate of transmission signal, the pulse recurrence frequency of transmission signal, transmitting letter
Number pulse width, transmission signal wavelength, the radar start working time, orbital angular momentum pattern count and circular loop antenna radius,
The orbital angular momentum is more than 0；The operational factor of the carrier aircraft equipment comprises at least：The flying speed of the carrier aircraft equipment, fly
Row height；
Scenario parameters determining module, the simulation parameter according to acquisition is configured as, determines the scene ginseng in target scene region
Number, the scenario parameters include：Distance is to point target number, orientation point target number, and distance is to point target interval and orientation
To point target interval, each target scattering coefficient；
Echo-signal acquisition module, it is configured as according to the simulation parameter and the scenario parameters, obtains electromagnetism vortex synthesis
Aperture radar artificial echo signal.
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108572363A (en) * | 2018-04-27 | 2018-09-25 | 中国人民解放军国防科技大学 | Electromagnetic vortex high-resolution imaging method based on sparse Bayesian learning |
| CN109490881A (en) * | 2018-11-21 | 2019-03-19 | 中国科学院电子学研究所 | Interference SAR measurement of higher degree system and measurement method based on vortex electromagnetic wave |
| CN109541594A (en) * | 2018-11-12 | 2019-03-29 | 中国人民解放军国防科技大学 | Stripe SAR three-dimensional imaging method based on vortex electromagnetic waves |
| CN110412571A (en) * | 2019-07-19 | 2019-11-05 | 西安电子科技大学 | Synthetic aperture radar three-dimensional imaging method based on electromagnetism vortex wave |
| CN110501707A (en) * | 2019-08-27 | 2019-11-26 | 中国人民解放军国防科技大学 | Electromagnetic vortex imaging method based on orbital angular momentum bimodal multiplexing |
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| CN110412571B (en) * | 2019-07-19 | 2023-03-14 | 西安电子科技大学 | Synthetic aperture radar three-dimensional imaging method based on electromagnetic vortex wave |
| CN110501707A (en) * | 2019-08-27 | 2019-11-26 | 中国人民解放军国防科技大学 | Electromagnetic vortex imaging method based on orbital angular momentum bimodal multiplexing |
| CN110501707B (en) * | 2019-08-27 | 2021-07-02 | 中国人民解放军国防科技大学 | Electromagnetic vortex imaging method based on orbital angular momentum bimodal multiplexing |
| CN113281743A (en) * | 2021-05-14 | 2021-08-20 | 合肥工业大学 | Rapid high-resolution imaging method based on OAM radar imaging system |
| CN114221138A (en) * | 2022-02-23 | 2022-03-22 | 北京芯可鉴科技有限公司 | Artificial electromagnetic super surface and manufacturing method thereof |
| CN114221138B (en) * | 2022-02-23 | 2022-04-29 | 北京芯可鉴科技有限公司 | Artificial electromagnetic super surface and manufacturing method thereof |
| CN114415181A (en) * | 2022-03-31 | 2022-04-29 | 南方海洋科学与工程广东省实验室(广州) | Method and device for generating original echo of synthetic aperture radar |
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